XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-193 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.3459 0.09957 0.09536 -0.1266 0.7829 0.0071 -16.500 -0.4025 0.08365 0.07912 -0.1354 0.7828 0.0068 -16.250 -0.4163 0.07675 0.07211 -0.1400 0.7826 0.0069 -16.000 -0.4322 0.06983 0.06502 -0.1448 0.7823 0.0069 -15.750 -0.4456 0.06381 0.05883 -0.1488 0.7821 0.0068 -15.500 -0.4480 0.05979 0.05473 -0.1517 0.7818 0.0070 -15.250 -0.4554 0.05536 0.05013 -0.1544 0.7814 0.0069 -15.000 -0.4597 0.05162 0.04625 -0.1565 0.7810 0.0069 -14.750 -0.4602 0.04855 0.04305 -0.1581 0.7806 0.0069 -14.500 -0.4589 0.04588 0.04029 -0.1594 0.7801 0.0070 -14.250 -0.4586 0.04323 0.03750 -0.1603 0.7796 0.0071 -14.000 -0.4539 0.04117 0.03534 -0.1609 0.7791 0.0071 -13.750 -0.4488 0.03925 0.03332 -0.1613 0.7785 0.0071 -13.500 -0.4445 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1.0307 0.03618 0.02824 -0.0450 0.0617 0.7089 10.750 1.0364 0.03773 0.02969 -0.0435 0.0435 0.7091 11.000 1.0465 0.03900 0.03096 -0.0425 0.0373 0.7093 11.250 1.0556 0.04038 0.03231 -0.0414 0.0268 0.7094 11.500 1.0638 0.04186 0.03376 -0.0403 0.0195 0.7096 11.750 1.0744 0.04319 0.03511 -0.0395 0.0169 0.7097 12.000 1.0849 0.04456 0.03651 -0.0387 0.0137 0.7099 12.250 1.0955 0.04594 0.03791 -0.0380 0.0117 0.7100 12.500 1.1047 0.04747 0.03947 -0.0373 0.0102 0.7102 12.750 1.1154 0.04889 0.04093 -0.0366 0.0096 0.7103 13.000 1.1255 0.05039 0.04248 -0.0361 0.0092 0.7106 13.250 1.1351 0.05197 0.04411 -0.0355 0.0089 0.7108 13.500 1.1444 0.05360 0.04579 -0.0349 0.0086 0.7110 13.750 1.1528 0.05536 0.04761 -0.0344 0.0084 0.7112 14.000 1.1620 0.05706 0.04937 -0.0340 0.0083 0.7114 14.250 1.1706 0.05886 0.05124 -0.0337 0.0081 0.7116 14.500 1.1781 0.06081 0.05326 -0.0333 0.0080 0.7118 14.750 1.1866 0.06268 0.05520 -0.0330 0.0079 0.7120 15.000 1.1932 0.06479 0.05739 -0.0328 0.0078 0.7122 15.250 1.2001 0.06690 0.05957 -0.0326 0.0077 0.7125 15.500 1.2065 0.06910 0.06184 -0.0325 0.0077 0.7129 15.750 1.2116 0.07150 0.06433 -0.0325 0.0075 0.7132 16.000 1.2176 0.07383 0.06674 -0.0325 0.0075 0.7135 16.250 1.2216 0.07645 0.06944 -0.0326 0.0074 0.7136 16.500 1.2269 0.07894 0.07201 -0.0328 0.0074 0.7138 16.750 1.2299 0.08177 0.07493 -0.0331 0.0073 0.7139 17.000 1.2342 0.08447 0.07770 -0.0334 0.0073 0.7141 17.250 1.2364 0.08749 0.08082 -0.0339 0.0072 0.7143 17.500 1.2397 0.09040 0.08380 -0.0344 0.0072 0.7144 17.750 1.2420 0.09349 0.08699 -0.0350 0.0072 0.7146 18.000 1.2442 0.09659 0.09018 -0.0357 0.0071 0.7147 18.250 1.2458 0.09984 0.09351 -0.0366 0.0071 0.7149 18.500 1.2480 0.10300 0.09676 -0.0374 0.0071 0.7151 18.750 1.2495 0.10631 0.10016 -0.0384 0.0071 0.7152 19.000 1.2512 0.10958 0.10351 -0.0395 0.0070 0.7154 19.250 1.2521 0.11299 0.10701 -0.0406 0.0070 0.7155